EP3564511A1 - Oil tank mount arrangement on a geared turbofan engine - Google Patents
Oil tank mount arrangement on a geared turbofan engine Download PDFInfo
- Publication number
- EP3564511A1 EP3564511A1 EP19175223.7A EP19175223A EP3564511A1 EP 3564511 A1 EP3564511 A1 EP 3564511A1 EP 19175223 A EP19175223 A EP 19175223A EP 3564511 A1 EP3564511 A1 EP 3564511A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- oil tank
- mount
- coupled
- bracket
- fan case
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
- F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/41—Movement of components with one degree of freedom
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/41—Movement of components with one degree of freedom
- F05D2250/411—Movement of components with one degree of freedom in rotation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/42—Movement of components with two degrees of freedom
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/43—Movement of components with three degrees of freedom
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the subject matter of the present disclosure generally relates to gas turbine engines and more particularly, to mounting an oil tank on a geared turbofan engine.
- a mounting system for mounting an oil tank on a structure of a gas turbine engine includes a first mount coupled between the oil tank and a first point on the structure.
- the first mount may be configured to fix the oil tank along one degree of freedom.
- the mounting system may also include a second mount coupled between the oil tank and a second point on the structure.
- the second mount may be configured to fix the oil tank along two degrees of freedom.
- the mounting system may include a third mount coupled between the oil tank and a third point on the structure.
- the third mount may be configured to fix the oil tank along three degrees of freedom.
- a method of supporting an oil tank on a structure of a gas turbine engine includes attaching a first support between the oil tank and the structure.
- the first support may constrain the oil tank in one degree of freedom.
- the method may include attaching a second support between the oil tank and the structure.
- the second support may constrain the oil tank in two degrees of freedom.
- the method may also include attaching a third support between the oil tank and the structure.
- the third support may constrain the oil tank in three degrees of freedom.
- a system for mounting an oil tank to a fan case of a gas turbine engine may include a tripod mount coupled between a leading side portion of the oil tank and a leading end component of the fan case.
- the system may also include a triangle mount coupled between a trailing side portion of the oil tank and the fan case.
- the system may further include a single link mount coupled between another trailing side portion of the oil tank and the fan case.
- mounts with limited degrees of freedom are used to allow movement of an oil tank attached to a fan case of an engine, while still completely constraining the oil tank.
- issues including , thermal expansion, vibration, twist, etc. are more severe than in other gas turbine engines, for example, those using all metal or metal alloy fan cases..
- an engine 100 may include a fan case 102 having a front 104 and a back 106 and may include a radial structure known as a B flange 108.
- an oil tank 110 with a leading side 112 and a trailing side 114.
- the leading side 112 and the trailing side 114 are used with respect to their position on the engine 100, and may for the purposes of this disclosure may include surfaces adjacent to the actual sidewalls of the oil tank 110 when discussing mounting points for various brackets and mounts.
- the oil tank 110 may be held on with mounts shown in more detail in the following illustrations.
- the oil tank 110 is aluminum with a coefficient of expansion of approximately 10 microinches/inch/°F.
- the fan case 102 may have a coefficient of expansion that is virtually zero, or even slightly negative. Therefore, in an embodiment, the oil tank 110 may grow as much as a sixteenth of an inch front-to-back (axially along the fan case 102) and a non-negligible amount top-to-bottom (radially along the fan case).
- Each physical body has six degrees of freedom with respect to another body, translation in the x, y, and z directions, and rotation about the x, y, and z axes.
- a body may be constrained in one or more degrees of freedom, for example, hinges between a door and door frame restricts the door to rotational movement in one axis but allows translation in the x and y directions.
- the system of mounts described below attach the oil tank 110 to a structure, such as the fan case 102, and constrain the oil tank 110 in one degree of freedom at one mount, two degrees of freedom at a second mount, and three degrees of freedom at a third mount.
- a structure such as the fan case 102
- the oil tank 110, or any body so attached will have some limited movement, but will be secured in place relative to the other body.
- the mounting system disclosed is suitable for use in coupling any two structures to each other, particularly in situations where a first structure has a different coefficient of expansion from the other structure.
- Fig. 2 is a simplified illustration of a mounting apparatus for the oil tank of Fig. 1 .
- the mounting technique may use a first mount 172, a second mount 174, and a third mount 176.
- the mounting technique is discussed in more detail below with respect to Figs. 3-5 .
- FIG. 3 the first mount 172 of Fig. 2 is shown in side view, according to an embodiment.
- a bracket 184 is shown mounted to a wall of the oil tank 110.
- Another bracket 190 is shown mounted to an outer surface of the fan case 102.
- a linkage 186 may be connected to the bracket 184 and bracket 190 via pin 188 and pin 192.
- the linkage 186 allows radial rotation, radial translation, and vertical translation of the oil tank 110 with respect to the fan case 102. Because of the elongate shape and mounting holes on each end, the linkage 186 is sometimes referred to as a dogbone link.
- the oil tank 110 is constrained from side-to-side translation (i.e., axial translation) with respect to the fan case 102.
- the bracket 184 and the bracket 190 may be attached by any of a number of known means, including, but not limited to, fasteners, welds, or molded into or glued onto respective the composite surfaces, sometimes called “bathtub mounts,” which may include threaded metal plates.
- Fig. 4 shows the second mount 174 of Fig. 2 in side view, according to an embodiment.
- a bracket 194 may be mounted to a wall of the oil tank 110 and coupled to a bracket 196 by a pin 198.
- the bracket 196 may be coupled to the outer surface of the fan case 102.
- the brackets 194 and 196 may be attached by any of a number of known means, including, but not limited to, fasteners, welds, or molded into or glued onto respective the composite surfaces, sometimes called "bathtub mounts," which may include threaded metal plates.
- the second mount 174 may allow only rotational movement of the oil tank 110 with respect to the fan case 102 and may be constrained in two degrees of freedom both axial and radial.
- Fig. 5 illustrates in more detail an embodiment of the oil-tank end of the first mount 172 of Fig. 3 and more generally, also illustrates an embodiment of the connections used at brackets 190 and 196.
- the bracket 184 on the oil tank 110 may be connected to the linkage 186 by a pin 188.
- a bushing 187 may be used to prevent wear on the lugs of the bracket 184.
- a rubber gasket 185 may be used to cushion the contact point between the linkage 186 and pin 188.
- the rubber gasket 185 may provide wear protection and add a level of shock absorption to the assembly.
- the pin 188, as well as pins 192 and 198 of Figs. 3 and 4 may be frangible pins.
- a secondary shaft 189 associated with each pin may remain, in a known manner, to keep the oil tank 110 coupled to the engine 100 after the release of energy associated with breaking the pin and the additional movement available to the oil tank 110.
- the third mount 176 may include a bracket 178 attached to the oil tank 110 and a mount 180 attached to the B flange 108 by a bolt or fastener 182.
- the third mount 176 allows rotational movement of the oil tank 110 around the axis of the bolt or fastener 182 but is constrained in three degrees of freedom, that is axial, radial, and height above the fan case 102 .
- Figs. 6a, 6b, and 6c are simplified illustrations of a second mounting technique for the oil tank 110 of Fig. 1 , according to various embodiments.
- Figs. 6a-6c illustrate various perspectives of a mount system with mounts only from the front 104 of the fan case 102 and the B flange 108, leaving the face of the fan case 102 clear. This avoids the need to provide the bathtub mounts on the face of the fan case 102 shown in the exemplary embodiment of Fig. 2 .
- three mounts are used, a first mount 201, a second mount 202, and a third mount 204.
- the first mount 201 may have a mounting bracket 206 coupled to the front 104 of the fan case 102.
- the mounting bracket 206 may be coupled to a base of a spherical joint 208 that is coupled at a free end to a tripod 210.
- a head 212 of the tripod 210 may be coupled to the second side of the spherical joint 208 and the head 212 may be attached to the two of the three tripod legs 214a and 214b.
- the third tripod leg 214c is connected to the head 212 by another spherical joint 215.
- a base end of each of the tripod legs 214a, 214b, and 214c may be coupled to separate points on the oil tank 110. Each base end may also include a spherical joint attachment.
- the first mount 201 allows no translation of the oil tank 110, but the arms of the tripod 210 can pivot as the oil tank 110 expands and contracts.
- the oil tank 110 is constrained in three degrees of freedom along the plane of the base triangle of the mount. That is, a leading side of the oil tank at the point of attachment to the tripod 210, cannot move radially, axially, or in height above the fan case, but still allows the depth of the oil tank to change and allows limited rotation of the oil tank with respect to the leading edge 104.
- the second mount 202 may include a spherical joint 216 with a base coupled to the oil tank 110 directly or via a bracket.
- Two legs 218a and 218b of a triangle support 218 may be coupled to the free end of the spherical joint 216 and to separate B flange mounts 220a and 220b, respectively.
- each B flange mount 220a and 220b may also include spherical joints.
- a third leg 218c of the triangle support 218 may be coupled between the B flange mounts 220a and 220b.
- the third leg 218c of the triangle support 218 may be accommodated by the B flange 108 itself without a separate third leg 218c.
- the second mount 202 may constrain the oil tank in two degrees of freedom in that a trailing side of the oil tank 110 may move axially closer to and farther from the B flange as the oil tank 110 expands and contracts, but the attachment point of the spherical joint 216 is restricted in the radial direction and height.
- the third mount 204 may include, as above, a spherical joint 222 mounted or coupled to the oil tank 1 10. A free end of the spherical joint 222 coupled by a rod or shaft 226 to a bracket 224 mounted on the B flange.
- the bracket 224 may also include a spherical joint.
- the third mount 204 is constrained in one degree of freedom and allows movement of the oil tank 110 both axially with respect to the B flange 108 and radially toward and away from the second mount 202.
- each of the three mounts can be described in terms of the motion that the mount allows and restricts with respect to its end points.
- the second mount 202 fixes the distance between the spherical mount 216 and each of the B-flange mounts 220a and 220b and keeps the spherical mount 216 a relatively fixed distance above the fan case 102.
- the clearance distance between the fan case 102 and a bottom surface of the oil tank 1 10 may vary as the oil tank expands and contracts in use.
- the triangular support 218 also fixes the radial relationship between the spherical mount 216 and the two B-flange mounts 220a and 220b so that, in the embodiment, the spherical mount 216 is fixed radially with respect to the fan case 110.
- the nature of the spherical mounts allows axial movement (toward and away from the front 104 of fan case 102) of the spherical mount 216 with respect to the B-flange mounts 220a and 220b as the oil tank 110 expands and contracts in width.
- the axial movement of the oil tank causes rotation of the triangular support 218 about an axis defined by the third leg 218c.
- the third mount 204 allows both radial motion and axial motion between the base spherical joint 224 and the oil tank spherical mount 222.
- the third mount 204 constrains the distance between the base spherical joint 224 and the oil tank spherical mount 222 at a fixed length equal to a length of the rod or shaft 226. Expansion and contraction of the oil tank 110 causes both axial and radial movement of the spherical mount 222.
- both the second mount 202 and the third mount 204 are placed at an acute angle with respect to the oil tank 110 and the fan case 102, expansion of the tank in the axial direction will cause the oil tank 100 to rise slightly as the respective mounts become more vertical. This slight rise may help to accommodate any increase in depth of the oil tank 110.
- the first mount 201 may constrain a leading edge of the oil tank 110 both axially and radially.
- the leg 214c due to the spherical mounts at both ends, allows the oil tank 110 to expand in depth while still contributing to the axial and radial constraint of the leading edge of the oil tank 110.
- a first mount constrains one point on the oil tank in both the horizontal and vertical
- a second mount constrains the tank in the vertical
- the third mount allows motion in both the horizontal and vertical.
- Each of the mounts contributes to constraining the height of the oil tank 110 above the fan case 102.
- any of the mounts described herein may be made of steel, composite material, or other suitable high strength materials, or a combination thereof.
- Fig. 7 illustrates a method 300 of attaching an oil tank 110 to a fan case 102 in an engine 100, such as a gas turbine engine.
- a first support may be attached between the oil tank 110 and the fan case 102.
- the first support may constrain the oil tank in three degrees of freedom as discussed above with respect to mounts 172 of Fig. 2 , and 201 of Fig. 6a .
- a second support may be attached between the oil tank 110 and the fan case 102 wherein the second support constrains the oil tank 110 in two degrees of freedom.
- the second support may include embodiments described above with respect to mounts 174 of Fig. 2 , and 202 of Fig. 6a .
- a third support may be attached between the oil tank 110 and the fan case 102.
- the third support may constrain the oil tank in three degrees of freedom so that in combination with the first support and the second support, the oil tank is fully captured but is not immovably attached to the fan case.
- the third support may include embodiments described above with respect to mounts 176 of Fig. 2 and 204 of Fig. 6a . Although certain embodiments of the oil tank mounting system are described above, other mechanical attachments that preserve the concept of increasing constraints to allow secure mounting without rigid attachment are possible.
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Abstract
Description
- The subject matter of the present disclosure generally relates to gas turbine engines and more particularly, to mounting an oil tank on a geared turbofan engine.
- It is desirable to mount an oil tank of a gas turbine engine on the fan case. This puts the oil tank forward of the high-heat areas of the engine and provides some level of ambient air cooling. It is also more easily reached for service and maintenance while freeing very limited mechanical space aft of the fan case. However, geared turbofan engines are characterized by large fan diameters that have driven fan cases to an increasing use of composites over traditional aluminum and other metals and alloys. Mounting the oil tank to the fan case is more difficult with a composite because of different coefficients of expansion between the tank and the fan case and the different profiles for deflection and loading under normal, limit, and ultimate scenarios.
- In a first embodiment, a mounting system for mounting an oil tank on a structure of a gas turbine engine includes a first mount coupled between the oil tank and a first point on the structure. The first mount may be configured to fix the oil tank along one degree of freedom. The mounting system may also include a second mount coupled between the oil tank and a second point on the structure. The second mount may be configured to fix the oil tank along two degrees of freedom. In addition, the mounting system may include a third mount coupled between the oil tank and a third point on the structure. The third mount may be configured to fix the oil tank along three degrees of freedom.
- In another embodiment, a method of supporting an oil tank on a structure of a gas turbine engine includes attaching a first support between the oil tank and the structure. The first support may constrain the oil tank in one degree of freedom. The method may include attaching a second support between the oil tank and the structure. The second support may constrain the oil tank in two degrees of freedom. The method may also include attaching a third support between the oil tank and the structure. The third support may constrain the oil tank in three degrees of freedom.
- In yet another embodiment, a system for mounting an oil tank to a fan case of a gas turbine engine may include a tripod mount coupled between a leading side portion of the oil tank and a leading end component of the fan case. The system may also include a triangle mount coupled between a trailing side portion of the oil tank and the fan case. The system may further include a single link mount coupled between another trailing side portion of the oil tank and the fan case.
- So that the manner in which the above recited concepts of the present disclosure may be understood in detail, a more particular description is provided by reference to the embodiments which are illustrated in the accompanying drawings. It is to be noted, however, that the appended drawings illustrate only typical embodiments and are therefore not to be considered limiting of its scope, for the concepts of the present disclosure may admit to other equally effective embodiments. Moreover, the drawings are not necessarily to scale, emphasis generally being placed upon illustrating the principles of certain embodiments.
- Thus, for further understanding of these concepts and embodiments, reference may be made to the following detailed description, read in connection with the drawings in which:
-
Fig. 1 illustrates a view of a gas turbine engine showing an oil tank mounted to a fan case, according to an embodiment; -
Fig. 2 is a simplified illustration of a first mounting technique for the oil tank ofFig. 1 , according to an embodiment; -
Fig. 3 is a side view illustration of one mount of the mounting technique shown inFig. 2 , according to an embodiment; -
Fig. 4 is a side view illustration of another mount of the mounting technique shown inFig. 2 , according to an embodiment; -
Fig. 5 is a cutaway view of a mount, according to an embodiment; -
Figs. 6a, 6b, and 6c are front, side, and bottom views, respectively, of a second mounting technique for the oil tank ofFig. 1 , according to an embodiment; and -
Fig. 7 is a process flow for mounting an oil tank to a fan case in a gas turbine engine, according to an embodiment. - In an embodiment, mounts with limited degrees of freedom are used to allow movement of an oil tank attached to a fan case of an engine, while still completely constraining the oil tank. In addition, with the use of composite or other special materials in air frames, structures, and engine cases, issues including , thermal expansion, vibration, twist, etc., are more severe than in other gas turbine engines, for example, those using all metal or metal alloy fan cases..
- Referring to
Fig. 1 , anengine 100, for example, a geared turbofan engine, may include afan case 102 having afront 104 and aback 106 and may include a radial structure known as aB flange 108. Also illustrated on theengine 100 in this embodiment is anoil tank 110 with a leadingside 112 and atrailing side 114. The leadingside 112 and thetrailing side 114 are used with respect to their position on theengine 100, and may for the purposes of this disclosure may include surfaces adjacent to the actual sidewalls of theoil tank 110 when discussing mounting points for various brackets and mounts. Theoil tank 110 may be held on with mounts shown in more detail in the following illustrations. In an embodiment, theoil tank 110 is aluminum with a coefficient of expansion of approximately 10 microinches/inch/°F. However, when manufactured using a composite, thefan case 102 may have a coefficient of expansion that is virtually zero, or even slightly negative. Therefore, in an embodiment, theoil tank 110 may grow as much as a sixteenth of an inch front-to-back (axially along the fan case 102) and a non-negligible amount top-to-bottom (radially along the fan case). - Using a system of mounts that does not attempt to prevent movement but still constrains the case to its location allows the
oil tank 110 to grow and contract while still being held in place. Each physical body has six degrees of freedom with respect to another body, translation in the x, y, and z directions, and rotation about the x, y, and z axes. A body may be constrained in one or more degrees of freedom, for example, hinges between a door and door frame restricts the door to rotational movement in one axis but allows translation in the x and y directions. - The system of mounts described below, in various embodiments, attach the
oil tank 110 to a structure, such as thefan case 102, and constrain theoil tank 110 in one degree of freedom at one mount, two degrees of freedom at a second mount, and three degrees of freedom at a third mount. The result is that theoil tank 110, or any body so attached, will have some limited movement, but will be secured in place relative to the other body. While in the following exemplary embodiments discuss mounting theoil tank 110 with respect to various physical features of thefan case 102, it should be understood that the mounting system disclosed is suitable for use in coupling any two structures to each other, particularly in situations where a first structure has a different coefficient of expansion from the other structure. -
Fig. 2 is a simplified illustration of a mounting apparatus for the oil tank ofFig. 1 . The mounting technique may use afirst mount 172, asecond mount 174, and athird mount 176. The mounting technique is discussed in more detail below with respect toFigs. 3-5 . - Turning to
Fig. 3 , thefirst mount 172 ofFig. 2 is shown in side view, according to an embodiment. Abracket 184 is shown mounted to a wall of theoil tank 110. Anotherbracket 190 is shown mounted to an outer surface of thefan case 102. Alinkage 186 may be connected to thebracket 184 andbracket 190 viapin 188 andpin 192. Thelinkage 186 allows radial rotation, radial translation, and vertical translation of theoil tank 110 with respect to thefan case 102. Because of the elongate shape and mounting holes on each end, thelinkage 186 is sometimes referred to as a dogbone link. However, theoil tank 110 is constrained from side-to-side translation (i.e., axial translation) with respect to thefan case 102. Thebracket 184 and thebracket 190 may be attached by any of a number of known means, including, but not limited to, fasteners, welds, or molded into or glued onto respective the composite surfaces, sometimes called "bathtub mounts," which may include threaded metal plates. -
Fig. 4 , shows thesecond mount 174 ofFig. 2 in side view, according to an embodiment. Abracket 194 may be mounted to a wall of theoil tank 110 and coupled to abracket 196 by apin 198. Thebracket 196 may be coupled to the outer surface of thefan case 102. As above, thebrackets second mount 174 may allow only rotational movement of theoil tank 110 with respect to thefan case 102 and may be constrained in two degrees of freedom both axial and radial. -
Fig. 5 illustrates in more detail an embodiment of the oil-tank end of thefirst mount 172 ofFig. 3 and more generally, also illustrates an embodiment of the connections used atbrackets bracket 184 on theoil tank 110 may be connected to thelinkage 186 by apin 188. Abushing 187 may be used to prevent wear on the lugs of thebracket 184. Arubber gasket 185 may be used to cushion the contact point between thelinkage 186 andpin 188. Therubber gasket 185 may provide wear protection and add a level of shock absorption to the assembly. In an embodiment, thepin 188, as well aspins Figs. 3 and 4 may be frangible pins. That is, they may break during some failure modes and allow energy to be absorbed by the act of breaking the pins and by the extended movement of theoil tank 110 with respect to thefan case 102. In an additional embodiment, asecondary shaft 189 associated with each pin may remain, in a known manner, to keep theoil tank 110 coupled to theengine 100 after the release of energy associated with breaking the pin and the additional movement available to theoil tank 110. - Returning to
Fig. 2 , thethird mount 176 may include abracket 178 attached to theoil tank 110 and amount 180 attached to theB flange 108 by a bolt orfastener 182. Thethird mount 176 allows rotational movement of theoil tank 110 around the axis of the bolt orfastener 182 but is constrained in three degrees of freedom, that is axial, radial, and height above thefan case 102 . -
Figs. 6a, 6b, and 6c are simplified illustrations of a second mounting technique for theoil tank 110 ofFig. 1 , according to various embodiments.Figs. 6a-6c illustrate various perspectives of a mount system with mounts only from thefront 104 of thefan case 102 and theB flange 108, leaving the face of thefan case 102 clear. This avoids the need to provide the bathtub mounts on the face of thefan case 102 shown in the exemplary embodiment ofFig. 2 . According to an embodiment, three mounts are used, afirst mount 201, asecond mount 202, and athird mount 204. - The
first mount 201 may have a mountingbracket 206 coupled to thefront 104 of thefan case 102. The mountingbracket 206 may be coupled to a base of a spherical joint 208 that is coupled at a free end to atripod 210. Ahead 212 of thetripod 210 may be coupled to the second side of the spherical joint 208 and thehead 212 may be attached to the two of the threetripod legs third tripod leg 214c is connected to thehead 212 by another spherical joint 215. A base end of each of thetripod legs oil tank 110. Each base end may also include a spherical joint attachment. In an embodiment, thefirst mount 201, allows no translation of theoil tank 110, but the arms of thetripod 210 can pivot as theoil tank 110 expands and contracts. Theoil tank 110 is constrained in three degrees of freedom along the plane of the base triangle of the mount. That is, a leading side of the oil tank at the point of attachment to thetripod 210, cannot move radially, axially, or in height above the fan case, but still allows the depth of the oil tank to change and allows limited rotation of the oil tank with respect to theleading edge 104. - The
second mount 202 may include a spherical joint 216 with a base coupled to theoil tank 110 directly or via a bracket. Twolegs triangle support 218 may be coupled to the free end of the spherical joint 216 and to separate B flange mounts 220a and 220b, respectively. In an embodiment, eachB flange mount third leg 218c of thetriangle support 218 may be coupled between the B flange mounts 220a and 220b. In an embodiment, thethird leg 218c of thetriangle support 218 may be accommodated by theB flange 108 itself without a separatethird leg 218c. Thesecond mount 202 may constrain the oil tank in two degrees of freedom in that a trailing side of theoil tank 110 may move axially closer to and farther from the B flange as theoil tank 110 expands and contracts, but the attachment point of the spherical joint 216 is restricted in the radial direction and height. - The
third mount 204 may include, as above, a spherical joint 222 mounted or coupled to theoil tank 1 10. A free end of the spherical joint 222 coupled by a rod orshaft 226 to abracket 224 mounted on the B flange. Thebracket 224 may also include a spherical joint. Thethird mount 204 is constrained in one degree of freedom and allows movement of theoil tank 110 both axially with respect to theB flange 108 and radially toward and away from thesecond mount 202. - With reference to
Figs. 6a, 6b, and 6c , each of the three mounts can be described in terms of the motion that the mount allows and restricts with respect to its end points. - In an embodiment, the
second mount 202 fixes the distance between thespherical mount 216 and each of the B-flange mounts fan case 102. The clearance distance between thefan case 102 and a bottom surface of theoil tank 1 10 may vary as the oil tank expands and contracts in use. Thetriangular support 218 also fixes the radial relationship between thespherical mount 216 and the two B-flange mounts spherical mount 216 is fixed radially with respect to thefan case 110. However, the nature of the spherical mounts allows axial movement (toward and away from thefront 104 of fan case 102) of thespherical mount 216 with respect to the B-flange mounts oil tank 110 expands and contracts in width. In this embodiment, the axial movement of the oil tank causes rotation of thetriangular support 218 about an axis defined by thethird leg 218c. - The
third mount 204 allows both radial motion and axial motion between the base spherical joint 224 and the oil tankspherical mount 222. Thethird mount 204 constrains the distance between the base spherical joint 224 and the oil tankspherical mount 222 at a fixed length equal to a length of the rod orshaft 226. Expansion and contraction of theoil tank 110 causes both axial and radial movement of thespherical mount 222. - Because both the
second mount 202 and thethird mount 204 are placed at an acute angle with respect to theoil tank 110 and thefan case 102, expansion of the tank in the axial direction will cause theoil tank 100 to rise slightly as the respective mounts become more vertical. This slight rise may help to accommodate any increase in depth of theoil tank 110. - The
first mount 201 may constrain a leading edge of theoil tank 110 both axially and radially. Theleg 214c, due to the spherical mounts at both ends, allows theoil tank 110 to expand in depth while still contributing to the axial and radial constraint of the leading edge of theoil tank 110. - In an embodiment, if the axial direction is defined as the horizontal, the radial direction is defined as the vertical, and a distance from a face of the fan case is defined as height, a first mount constrains one point on the oil tank in both the horizontal and vertical, a second mount constrains the tank in the vertical, and the third mount allows motion in both the horizontal and vertical. Each of the mounts contributes to constraining the height of the
oil tank 110 above thefan case 102. - As would be understood by one of ordinary skill in the art, any of the mounts described herein may be made of steel, composite material, or other suitable high strength materials, or a combination thereof.
-
Fig. 7 illustrates amethod 300 of attaching anoil tank 110 to afan case 102 in anengine 100, such as a gas turbine engine. At ablock 302, a first support may be attached between theoil tank 110 and thefan case 102. The first support may constrain the oil tank in three degrees of freedom as discussed above with respect tomounts 172 ofFig. 2 , and 201 ofFig. 6a . - At a
block 304, a second support may be attached between theoil tank 110 and thefan case 102 wherein the second support constrains theoil tank 110 in two degrees of freedom. The second support may include embodiments described above with respect tomounts 174 ofFig. 2 , and 202 ofFig. 6a . - At a
block 306, a third support may be attached between theoil tank 110 and thefan case 102. The third support may constrain the oil tank in three degrees of freedom so that in combination with the first support and the second support, the oil tank is fully captured but is not immovably attached to the fan case. The third support may include embodiments described above with respect tomounts 176 ofFig. 2 and 204 ofFig. 6a . Although certain embodiments of the oil tank mounting system are described above, other mechanical attachments that preserve the concept of increasing constraints to allow secure mounting without rigid attachment are possible. - In each of the above designs, by constraining the
oil tank 110 at three points with one, two, and three degrees of freedom constrained, respectively at each point, the oil tank is fully captured, but still moveable to accommodate changes due to pressure, thermal expansion, vibration, etc. The system and methods discussed above are relevant to applications on geared turbofan engines where large fan case diameters and the use of composite materials makes traditional oil tank mounting problematic. The use of these techniques to allow continued mounting of the oil tank on the fan case or other structure in the face of these problems retains the benefits of space utilization, maintenance access, and cooling enabled by this forward mounting position. - While the present disclosure has shown and described details of exemplary embodiments, it will be understood by one skilled in the art that various changes in detail may be effected therein without departing from the spirit and scope of the disclosure as defined by claims that may be supported by the written description and drawings. Further, where these exemplary embodiments (and other related derivations) are described with reference to a certain number of elements it will be understood that other exemplary embodiments may be practiced utilizing either less than or more than the certain number of elements. The following clauses set out features of the invention which may or may not presently be claimed in this application, but which may form the basis for future amendment or a divisional application.
- 1. A mounting system for mounting an oil tank on a structure of a gas turbine engine, the mounting system comprising:
- a first mount coupled between the oil tank and a first point on the structure, the first mount configured to fix the oil tank along one degree of freedom;
- a second mount coupled between the oil tank and a second point on the structure, the second mount configured to fix the oil tank along two degrees of freedom; and
- a third mount coupled between the oil tank and a third point on the structure, the third mount configured to fix the oil tank along three degrees of freedom.
- 2. The mounting system of
clause 1, wherein the structure is a fan case and the third mount is configured to be fixed to a B flange of the fan case. - 3. The mounting system of
clause 1, wherein:
the first mount includes a link with first end bore at one end of the link and second end bore at an opposite end of the link, with a rubber bushing disposed in each end bore, a first pin placed through the first end bore and a first rubber bushing and directly coupled to a bracket configured to be fixed to the structure and a second pin rotatably disposed through the second end bore and a second rubber bushing, the second pin directly coupled to a bracket configured to be mounted to the oil tank. - 4. The mounting system of
clause 3, wherein:
the second mount includes a first bracket configured to be coupled to the oil tank and a second bracket configured to be coupled to the structure, the bracket including a rubber bushing disposed in a bore of the bracket and a pin rotatably disposed through the rubber bushing. - 5. The mounting system of clause 4, wherein:
the third mount includes a bracket configured to be attached to the oil tank and a rubber mount configured to be attached to the structure, the bracket fixedly attached to the rubber mount. - 6. The mounting system of
clause 1, wherein the first mount includes a linkage with bores on each end, a first bore on a first linkage end of the linkage coupled via a pin to a first bracket configured to be attached to the structure and a second bore on a second end coupled via a second pin to an oil tank bracket configured to be attached to the oil tank. - 7. The mounting system of clause 6, wherein the second mount includes a second bracket configured to be attached to the structure, the second bracket hingedly coupled via a third pin to a second oil tank bracket that is configured to be attached to the oil tank.
- 8. The mounting system of clause 7, wherein the third mount includes a bracket configured to be attached to the oil tank and configured to be bolted to an attachment point on the structure.
- 9. The mounting system of clause 7, wherein the first pin, second pin, and third pins are frangible pins.
- 10. The mounting system of
clause 1, wherein the structure is a fan case and the first mount includes a bracket configured to be coupled to a leading edge of the fan case and to a first side of a spherical joint, an opposite side of the spherical joint coupled to a head of a tripod, wherein each leg of the tripod is configured to be separately coupled to different points on the oil tank. - 11. The mounting system of clause 10, wherein the second mount includes a triangle coupler with both ends of a base leg of the triangle coupler configured to be coupled to the fan case via separate spherical mounts and a head end of the triangle coupler configured to be coupled to the oil tank via another spherical mount.
- 12. The mounting system of clause 11, wherein the third mount is a dogbone link with a first end configured to be coupled via a pin to the oil tank and a second end configured to be coupled via another pin to the fan case.
- 13. The mounting system of
clause 1, wherein at least two of the first point, the second point, and the third point are at opposite ends of the oil tank. - 14. A method of supporting an oil tank on a structure of a gas turbine engine, the method comprising:
- attaching a first support between the oil tank and the structure, the first support constraining the oil tank in one degree of freedom;
- attaching a second support between the oil tank and the structure, the second support constraining the oil tank in two degrees of freedom; and
- attaching a third support between the oil tank and the structure, the third support constraining the oil tank in three degrees of freedom.
- 15. The method of clause 14, wherein each of the three supports includes a rubber portion and a metallic portion.
- 16. The method of clause 14, wherein attaching the first support comprises:
- coupling a first bracket that is configured to be fixedly attached to the structure to a first end of a dogbone link via a first pin;
- coupling a second bracket that is configured to be fixedly attached to the oil tank to a second end of the dogbone link via a second pin.
- 17. The method of clause 16, wherein the first pin and the second pin are frangible pins.
- 18. A system for mounting an oil tank to a fan case of a gas turbine engine, the system comprising:
- a tripod mount coupled between a leading side portion of the oil tank and a leading end component of the fan case;
- a triangle mount coupled between a trailing side portion of the oil tank and the fan case; and
- a single link mount coupled between another trailing side portion of the oil tank and the fan case.
- 19. The system of clause 18, wherein the tripod mount comprises a tripod with each leg of the tripod coupled to the leading side portion of the oil tank, a head of the tripod coupled to a proximal end of a spherical joint, and a bracket coupled to the leading end component of the fan case coupled to a distal end of the spherical joint.
- 20. The system of clause 19, wherein the tripod is made of steel.
Claims (15)
- A mounting system for mounting an oil tank (110) on a structure of a gas turbine engine, the mounting system comprising:a first mount (172;201) coupled between the oil tank (110) and a first point on the structure, the first mount (172;201) configured to fix the oil tank (110) along one degree of freedom;a second mount (174;202) coupled between the oil tank (110) and a second point on the structure, the second mount (174;202) configured to fix the oil tank (110) along two degrees of freedom; anda third mount (176;204) coupled between the oil tank (110) and a third point on the structure, the third mount (176;204) configured to fix the oil tank (110) along three degrees of freedom.
- The mounting system of claim 1, wherein the structure is a fan case (102) and the third mount (176;204) is configured to be fixed to a B flange (108) of the fan case (102).
- The mounting system of claim 1, wherein:
the first mount (172) includes a link (186) with first end bore at one end of the link and second end bore at an opposite end of the link, with a rubber bushing (187) disposed in each end bore, a first pin (192) placed through the first end bore and a first rubber bushing and directly coupled to a bracket (190) configured to be fixed to the structure and a second pin (188) rotatably disposed through the second end bore and a second rubber bushing, the second pin (188) directly coupled to a bracket (184) configured to be mounted to the oil tank (110). - The mounting system of claim 3, wherein:
the second mount (174) includes a first bracket (194) configured to be coupled to the oil tank (110) and a second bracket (196) configured to be coupled to the structure, the bracket including a rubber bushing disposed in a bore of the bracket and a pin (198) rotatably disposed through the rubber bushing. - The mounting system of claim 4, wherein:
the third mount (176) includes a bracket (178) configured to be attached to the oil tank (110) and a rubber mount (180) configured to be attached to the structure, the bracket (178) fixedly attached to the rubber mount (180). - The mounting system of claim 1, wherein:
the first mount (172) includes a linkage (186) with bores on each end, a first bore on a first linkage end of the linkage (186) coupled via a pin (192) to a first bracket (190) configured to be attached to the structure and a second bore on a second end coupled via a second pin (188) to an oil tank bracket (184) configured to be attached to the oil tank (110). - The mounting system of claim 6, wherein the second mount (174) includes a second bracket (196) configured to be attached to the structure, the second bracket (196) hingedly coupled via a third pin (198) to a second oil tank bracket (194) that is configured to be attached to the oil tank (110).
- The mounting system of claim 7, wherein the third mount (176) includes a bracket (178) configured to be attached to the oil tank (110) and configured to be bolted to an attachment point on the structure.
- The mounting system of claim 7, wherein the first pin (192), second pin (188), and third pins (198) are frangible pins.
- The mounting system of claim 1, wherein the structure is a fan case (102) and the first mount (201) includes a bracket (206) configured to be coupled to a leading edge of the fan case (102) and to a first side of a spherical joint (208), an opposite side of the spherical joint (208) coupled to a head (212) of a tripod (210), wherein each leg (214) of the tripod (210) is configured to be separately coupled to different points on the oil tank (110).
- The mounting system of claim 10, wherein the second mount (202) includes a triangle coupler (218) with both ends of a base leg (218c) of the triangle coupler (218) configured to be coupled to the fan case (102) via separate spherical mounts and a head end of the triangle coupler (218) configured to be coupled to the oil tank (110) via another spherical mount (216).
- The mounting system of claim 11, wherein the third mount (204) is a dogbone link with a first end configured to be coupled via a pin to the oil tank (210) and a second end configured to be coupled via another pin to the fan case (102).
- The mounting system of claim 1, wherein at least two of the first point, the second point, and the third point are at opposite ends of the oil tank (110).
- A system for mounting an oil tank (110) to a fan case (102) of a gas turbine engine, the system comprising:a tripod mount (201) coupled between a leading side portion of the oil tank (110) and a leading end component of the fan case (102);a triangle mount (202) coupled between a trailing side portion of the oil tank (110) and the fan case (102); anda single link mount (204) coupled between another trailing side portion of the oil tank (110) and the fan case (102).
- The system of claim 14, wherein the tripod mount (201) comprises a tripod (208) with each leg (214) of the tripod (208) coupled to the leading side portion of the oil tank (110), a head (212) of the tripod (208) coupled to a proximal end of a spherical joint (212), and a bracket (206) coupled to the leading end component of the fan case (102) coupled to a distal end of the spherical joint (212), and optionally wherein the tripod (210) is made of steel.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201361897020P | 2013-10-29 | 2013-10-29 | |
EP14857461.9A EP3063390B1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
PCT/US2014/039296 WO2015065525A1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
Related Parent Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14857461.9A Division EP3063390B1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
EP14857461.9A Division-Into EP3063390B1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
Publications (1)
Publication Number | Publication Date |
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EP3564511A1 true EP3564511A1 (en) | 2019-11-06 |
Family
ID=53004901
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
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EP14857461.9A Active EP3063390B1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
EP19175223.7A Pending EP3564511A1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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EP14857461.9A Active EP3063390B1 (en) | 2013-10-29 | 2014-05-23 | Oil tank mount arrangement on a geared turbofan engine |
Country Status (3)
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US (2) | US9951655B2 (en) |
EP (2) | EP3063390B1 (en) |
WO (1) | WO2015065525A1 (en) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
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EP3063390B1 (en) | 2013-10-29 | 2019-07-03 | United Technologies Corporation | Oil tank mount arrangement on a geared turbofan engine |
GB201611801D0 (en) * | 2016-07-07 | 2016-08-17 | Rolls Royce Plc | A mounting bracket |
BE1024639B1 (en) * | 2016-10-13 | 2018-05-16 | Safran Aero Boosters S.A. | TURBOMACHINE OIL TANK |
GB201621455D0 (en) | 2016-12-16 | 2017-02-01 | Rolls Royce Plc | Mount Structure |
FR3063787B1 (en) * | 2017-03-09 | 2021-04-23 | Safran Aircraft Engines | METHOD OF CONTROLLING VIBRATIONS IN A TURBOMACHINE PROPELLER ASSEMBLY |
GB201805930D0 (en) * | 2018-04-10 | 2018-05-23 | Rolls Royce Plc | Tank Assembly |
FR3099790B1 (en) * | 2019-08-09 | 2021-07-16 | Safran Aircraft Engines | Device for attaching an air supply unit to a cooling device for a turbomachine casing |
FR3099800B1 (en) * | 2019-08-09 | 2021-07-09 | Safran Aircraft Engines | Device for attaching an air supply unit to a cooling device for a turbomachine casing |
FR3099791B1 (en) * | 2019-08-09 | 2021-07-16 | Safran Aircraft Engines | Device for attaching an air supply unit to a cooling device for a turbomachine casing |
US11408345B2 (en) * | 2019-08-29 | 2022-08-09 | Rolls-Royce Corporation | Oil tank for geared turbofan engine |
US11422021B2 (en) | 2019-11-25 | 2022-08-23 | Rolls-Royce Corporation | Oil quantity measurement apparatus and method |
US11530633B2 (en) | 2019-12-05 | 2022-12-20 | Rolls-Royce Corporation | Efficient grounding of electrical connection with challenging bonding path |
US11674414B2 (en) | 2021-03-19 | 2023-06-13 | Pratt & Whitney Canada Corp. | Gas turbine engine and mount assembly therefor |
US11486271B1 (en) * | 2021-10-15 | 2022-11-01 | Pratt & Whitney Canada Corp. | Adjustable mount for engine accessory |
CN114087071B (en) * | 2021-11-16 | 2023-04-18 | 中国航发沈阳发动机研究所 | Lubricating oil tank mounting and fixing structure |
US20240110507A1 (en) * | 2022-09-30 | 2024-04-04 | General Electric Company | Conformal structure for a gas turbine engine |
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EP3063390B1 (en) | 2013-10-29 | 2019-07-03 | United Technologies Corporation | Oil tank mount arrangement on a geared turbofan engine |
-
2014
- 2014-05-23 EP EP14857461.9A patent/EP3063390B1/en active Active
- 2014-05-23 US US15/032,233 patent/US9951655B2/en active Active
- 2014-05-23 EP EP19175223.7A patent/EP3564511A1/en active Pending
- 2014-05-23 WO PCT/US2014/039296 patent/WO2015065525A1/en active Application Filing
-
2018
- 2018-04-20 US US15/958,527 patent/US10577979B2/en active Active
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US4377933A (en) * | 1980-06-30 | 1983-03-29 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Reservoir with an antivibration suspension |
US20070125087A1 (en) * | 2005-12-01 | 2007-06-07 | Hamilton Sundstrand | Gas turbine engine auxiliary component mount |
US20130042630A1 (en) * | 2011-08-19 | 2013-02-21 | United Technologies Corporation | Gas turbine engine accessory mount |
Also Published As
Publication number | Publication date |
---|---|
US20180245484A1 (en) | 2018-08-30 |
EP3063390A1 (en) | 2016-09-07 |
WO2015065525A1 (en) | 2015-05-07 |
EP3063390B1 (en) | 2019-07-03 |
US9951655B2 (en) | 2018-04-24 |
US10577979B2 (en) | 2020-03-03 |
EP3063390A4 (en) | 2017-03-29 |
US20160273389A1 (en) | 2016-09-22 |
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